Turbine nozzle airfoil profile

ABSTRACT

The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

FIELD

The present application relates generally to a turbine nozzle for a gas turbine engine, and more particularly relates to a turbine nozzle airfoil profile for a turbine nozzle.

BACKGROUND

Some aircraft and/or power plant systems, for example certain jet aircraft, nuclear, simple cycle and combined cycle power plant systems, employ turbines (also referred to as turbomachines) in their design and operation. Some of these turbines employ airfoils (e.g., stator vanes or nozzles and rotor blades.) which during operation are exposed to fluid flows. These airfoils are configured to aerodynamically interact with the fluid flows and generate energy (e.g., creating thrust, turning kinetic energy to mechanical energy, thermal energy to mechanical energy, etc.) from these fluid flows as part of power generation. As a result of this interaction and conversion, the aerodynamic characteristics and losses of these airfoils have an impact on system and turbine operation, performance, thrust, efficiency, and power.

BRIEF DESCRIPTION

Aspects and advantages are set forth below in the following description, or may be obvious from the description, or may be learned through practice.

The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

The present application further provides a turbine nozzle including an airfoil having a suction-side uncoated nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance. The airfoil profile sections at the Z distances may be joined smoothly with one another to form a complete suction-side airfoil shape. The X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil.

The present application further provides a turbine with a number of turbine nozzles having an airfoil having an airfoil shape. The airfoils having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance. The airfoil profile sections at the Z distances may be joined smoothly with one another to form a complete airfoil shape.

Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of various embodiments, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:

FIG. 1 is a schematic representation of an exemplary turbine having multiple stages with each stage including alternating rows of turbine rotor blades and turbine nozzles according to at least one embodiment of the present disclosure;

FIG. 2 is a perspective view of an exemplary turbine nozzle according to at least one embodiment of the present disclosure; and

FIG. 3 provides a cross-sectional view of an airfoil portion of the turbine nozzle of FIG. 2.

DETAILED DESCRIPTION

Referring now to the drawings, particularly to FIG. 1, there is illustrated an exemplary turbine 10 of a gas turbine 12 including a plurality of turbine stages arranged in serial flow order. Each stage of the turbine includes a row of turbine nozzles or vanes disposed axially adjacent to a corresponding row of turbine rotor blades. Four stages are illustrated in FIG. 1. The exact number of stages of the turbine 10 is a choice of engineering design, and may be more or less than the four stages illustrated in FIG. 1. The four stages are merely exemplary of one turbine design, and are not intended to limit the presently claimed turbine rotor blade in any manner.

The first stage comprises a plurality of turbine nozzles or vanes 100 and a plurality of turbine rotor blades 150. The turbine nozzles 100 are annularly arranged about an axis of a turbine rotor 14. The turbine rotor blades 150 are annularly arranged about and coupled to the turbine rotor 14. A second stage of the turbine 12 includes a plurality of turbine nozzles 200 annularly arranged about the axis of the turbine rotor 14 and a plurality of turbine rotor blades 250 annularly arranged about and coupled to the turbine rotor 14. The turbine nozzles 200 may be coupled to a casing of the turbine 12.

As shown in FIG. 1, a third stage of the turbine 12 includes a plurality of turbine nozzles 300 annularly arranged about the axis of the turbine rotor 14 and a plurality of turbine rotor blades 350 annularly arranged about and coupled to the turbine rotor 14. The turbine nozzles 300 may be coupled to the casing of the turbine 12. In particular embodiments, the turbine 12 includes a fourth stage which includes plurality of turbine nozzles 400 annularly arranged about the axis of the turbine rotor 14 and a plurality of turbine rotor blades 450 annularly arranged about and coupled to the turbine rotor 14. The fourth stage turbine nozzles 400 may be coupled to the casing of the turbine 12.

It will be appreciated that the turbine nozzles 100, 200, 300 and 400 and turbine rotor blades 150, 250, 350 and 450 are disposed or at least partially disposed within a hot gas path 18 of the turbine 12. The various stages of the turbine 10 at least partially define the hot gas path 18 through which combustion gases, as indicated by arrows 20, flow during operation of the gas turbine 12.

FIG. 2 provides a perspective view of an exemplary turbine nozzle 50 as may be incorporated in any stage of the turbine 12. FIG. 3 provides a cross-sectional top view of an airfoil 52 of the turbine nozzle 50 shown in FIG. 2. In one embodiment the turbine nozzle 50 as provided in Table I below is representative of turbine nozzle 400 of the plurality of turbine nozzles 400 of the fourth stage as shown in FIG. 1. As shown in FIGS. 2 and 3 collectively, the turbine nozzle 50 airfoil 52 includes a pressure-side wall 54 and an opposing suction-side wall 56. The pressure-side wall 54 and the suction-side wall 56 meet or intersect at a leading edge 58 and at a trailing edge 60 of the airfoil 52. A chord line 62 extends between the leading edge 58 and the trailing edge 60 such that pressure and suction-side walls 54, 56 can be said to extend in chord or chordwise between the leading edge 58 and the trailing edge 60.

As shown in FIG. 2, the airfoil 52 includes a root or first end 64 which intersects with and extends radially outwardly from an inner band 66 of the turbine nozzle 50. The airfoil 52 terminates radially at a second end or tip 68 of the airfoil 52. The second end 68 intersects with and extends radially inwardly from an outer band 70 of the turbine nozzle 50. The pressure and suction-side walls 54, 56 can be said to extend in height and/or span or in a span-wise direction 72 between the root 64 and/or the inner band 66 and the second end 68 or the outer band 70. In other words, each turbine nozzle 50 includes an airfoil 52 having opposing pressure and suction-side walls 54, 56 that extend in chord or chordwise 62 between opposing leading and trailing edges 58, 60 and that extend in span or span-wise 72 between the root 64 and the second end 68 of the airfoil 52.

In particular configurations, the airfoil 52 may include a fillet 74 formed between the inner band 66 and the airfoil 52 proximate to the root 64. The fillet 74 can include a weld or braze fillet, which can be formed via conventional MIG welding, TIG welding, brazing, etc., and can include a profile that can reduce fluid dynamic losses as a result of the presence of fillet 74. In particular embodiments, the inner band 66, airfoil 52 and the fillet 74 can be formed as a single component, such as by casting and/or machining and/or 3D printing and/or any other suitable technique now known or later developed and/or discovered.

The airfoil 52 of the turbine nozzle 50 has a profile at any cross-section taken between the inner band 66 or the root 64 and the second end 68. The X, Y, and Z values are given in Table I as percentage values of the airfoil length or height/span. As one example only, the height or radial span of the airfoil 52 of turbine nozzle 50 may be from about 5 inches to about 50 inches (about 12 centimeters to about 127 centimeters). However, it is to be understood that heights below or above this range may also be employed as desired in the specific application.

The gas turbine hot gas path 18 requires airfoils 52 that meet system requirements of aerodynamic and mechanical blade loading and efficiency. To define the airfoil shape of each turbine nozzle airfoil 52, there is a unique set or loci of points in space that meet the stage requirements and can be manufactured. These unique loci of points meet the requirements for stage efficiency and are arrived at by iteration between aerodynamic and mechanical loadings enabling the turbine to run in an efficient, safe and smooth manner. These points are unique and specific to the system.

The loci that defines the turbine nozzle airfoil profile includes a set of about 2,200 points with X, Y and Z dimensions relative to a reference origin coordinate system. The Cartesian coordinate system of X, Y and Z values given in Table I below defines the profile of the turbine nozzle airfoil at various locations along its length. Table I lists data for a non-coated airfoil. The envelope/tolerance for the coordinates is about +/−5% in a direction normal to any airfoil surface location and/or about +/−5% of the chord 62 in a direction nominal to any airfoil surface location. The point data origin 76 is defined at or proximate to the leading edge 58 of the airfoil 52 and at or proximate to the root 64.

The coordinate values for the X, Y and Z coordinates are set forth in non-dimensionalized units by the values provided in Table I although other units of dimensions may be used when the values are appropriately converted. The X, Y and Z values set forth in Table I are also expressed in non-dimensional form (X, Y, and Z) from 0% to 100% of the height or span of the airfoil 52. As one example only, the Cartesian coordinate values of X, Y and Z may be convertible to dimensional distances by multiplying the X, Y and Z values by a height of the airfoil at the leading edge 58 and multiplying by a constant number (e.g., 100). As one example only, the Cartesian coordinate values of X, Y and Z may be convertible to dimensional distances by multiplying the X, Y and Z values by a height of the airfoil at the trailing edge 60 and multiplying by a constant number (e.g., 100).

To convert the Z value to a Z coordinate value, e.g., in inches, the non-dimensional Z value given in Table I is multiplied by the Z length of the airfoil in inches. As described above, the Cartesian coordinate system has orthogonally-related X, Y and Z axes and the X axis lies generally parallel to the turbine rotor centerline, i.e., the rotary axis and a positive X coordinate value is axial toward an exhaust end of the turbine 14. The positive Y coordinate value extends tangentially in the direction of rotation of the rotor shaft 14 and the positive Z coordinate value is radially outwardly toward the second end 68 of the airfoil 52. All the values in Table I are given at room temperature and are non-filleted.

By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the profile section or airfoil shape of the airfoil 52 of the turbine nozzle 50, at each Z distance along the length of the airfoil 52 can be ascertained. By connecting the X and Y values with smooth continuing arcs, each profile section at each distance Z is fixed. The airfoil profiles of the various surface locations between the distances Z are determined by smoothly connecting the adjacent profile sections to one another to form the airfoil profile.

The Table I values are generated and shown to four decimal places for determining the profile of the airfoil. As the turbine nozzle surface heats up during operation of the turbine 14, mechanical stresses and elevated temperatures will cause a change in the X, Y and Z values. Accordingly, the values for the profile given in Table I represent ambient, non-operating or non-hot conditions (e.g., room temperature) and are for an uncoated airfoil.

There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual profile of the airfoil 52. Each section is joined smoothly with the other sections to form the complete airfoil shape. It will therefore be appreciated that +/− typical manufacturing tolerances, i.e., +/− values, including any coating thicknesses, are additive to the X and Y values given in Table I below. Accordingly, a distance of +/−5% in a direction normal to any surface location along the airfoil profile defines an airfoil profile envelope for this particular turbine nozzle airfoil design and turbine, i.e., a range of variation between measured points on the actual airfoil surface at nominal cold or room temperature and the ideal position of those points as given in the Table below at the same temperature. The data is scalable and the geometry pertains to all aerodynamic scales, at above and/or below 3000 RPM. The design of the airfoil 52 of the turbine nozzle 50 is robust to this range of variation without impairment of mechanical and aerodynamic functions.

TABLE I SUCTION-SIDE PRESSURE-SIDE X (%) Y (%) Z (%) N X (%) Y (%) Z (%) 0.0000 0.0000 0.0000 1 0.0000 0.0000 0.0000 −0.1468 −0.3998 0.0000 2 0.1871 0.2777 0.0000 −0.2206 −0.8187 0.0000 3 0.4405 0.4983 0.0000 −0.2127 −1.2445 0.0000 4 0.7294 0.6699 0.0000 −0.1221 −1.6606 0.0000 5 1.0370 0.8056 0.0000 0.0383 −2.0548 0.0000 6 1.3554 0.9141 0.0000 0.2538 −2.4223 0.0000 7 1.6802 1.0023 0.0000 0.5107 −2.7626 0.0000 8 2.0085 1.0745 0.0000 0.7976 −3.0775 0.0000 9 2.3397 1.1339 0.0000 1.1080 −3.3695 0.0000 10 2.6725 1.1834 0.0000 1.4360 −3.6420 0.0000 11 3.0064 1.2237 0.0000 1.7763 −3.8986 0.0000 12 3.3408 1.2568 0.0000 2.1274 −4.1404 0.0000 13 3.6764 1.2840 0.0000 2.4873 −4.3686 0.0000 14 4.0119 1.3063 0.0000 2.8560 −4.5833 0.0000 15 4.3479 1.3255 0.0000 3.2327 −4.7828 0.0000 16 4.6838 1.3430 0.0000 3.6169 −4.9667 0.0000 17 5.0198 1.3594 0.0000 4.0091 −5.1347 0.0000 18 5.3557 1.3765 0.0000 4.4077 −5.2855 0.0000 19 5.6917 1.3945 0.0000 4.8123 −5.4196 0.0000 20 6.0272 1.4148 0.0000 5.2225 −5.5353 0.0000 21 6.3628 1.4384 0.0000 5.6374 −5.6330 0.0000 22 6.6979 1.4655 0.0000 6.0564 −5.7120 0.0000 23 7.0331 1.4970 0.0000 6.4781 −5.7727 0.0000 24 7.3675 1.5333 0.0000 6.9026 −5.8142 0.0000 25 7.7010 1.5752 0.0000 7.3284 −5.8365 0.0000 26 8.0342 1.6227 0.0000 7.7545 −5.8405 0.0000 27 8.3662 1.6762 0.0000 8.1806 −5.8253 0.0000 28 8.6973 1.7356 0.0000 8.6055 −5.7918 0.0000 29 9.0273 1.8019 0.0000 9.0285 −5.7400 0.0000 30 9.3557 1.8741 0.0000 9.4490 −5.6701 0.0000 31 9.6828 1.9531 0.0000 9.8664 −5.5836 0.0000 32 10.0080 2.0385 0.0000 10.2797 −5.4798 0.0000 33 10.3316 2.1298 0.0000 10.6891 −5.3593 0.0000 34 10.6536 2.2276 0.0000 11.0929 −5.2237 0.0000 35 10.9736 2.3317 0.0000 11.4915 −5.0728 0.0000 36 11.2916 2.4415 0.0000 11.8845 −4.9073 0.0000 37 11.6076 2.5568 0.0000 12.2711 −4.7281 0.0000 38 11.9212 2.6777 0.0000 12.6518 −4.5354 0.0000 39 12.2332 2.8041 0.0000 13.0252 −4.3303 0.0000 40 12.5428 2.9358 0.0000 13.3919 −4.1129 0.0000 41 12.8501 3.0727 0.0000 13.7518 −3.8842 0.0000 42 13.1549 3.2143 0.0000 14.1041 −3.6444 0.0000 43 13.4577 3.3607 0.0000 14.4496 −3.3947 0.0000 44 13.7582 3.5124 0.0000 14.7876 −3.1345 0.0000 45 14.0558 3.6688 0.0000 15.1180 −2.8656 0.0000 46 14.3515 3.8296 0.0000 15.4412 −2.5875 0.0000 47 14.6444 3.9951 0.0000 15.7572 −2.3010 0.0000 48 14.9348 4.1647 0.0000 16.0656 −2.0066 0.0000 49 15.2225 4.3391 0.0000 16.3664 −1.7049 0.0000 50 15.5078 4.5174 0.0000 16.6601 −1.3957 0.0000 51 15.7903 4.7002 0.0000 16.9466 −1.0801 0.0000 52 16.0700 4.8865 0.0000 17.2255 −0.7577 0.0000 53 16.3473 5.0772 0.0000 17.4972 −0.4293 0.0000 54 16.6218 5.2715 0.0000 17.7621 −0.0950 0.0000 55 16.8939 5.4694 0.0000 18.0195 0.2446 0.0000 56 17.1632 5.6709 0.0000 18.2696 0.5897 0.0000 57 17.4297 5.8760 0.0000 18.5130 0.9396 0.0000 58 17.6939 6.0847 0.0000 18.7496 1.2943 0.0000 59 17.9552 6.2962 0.0000 18.9802 1.6530 0.0000 60 18.2138 6.5112 0.0000 19.2053 2.0149 0.0000 61 18.4699 6.7295 0.0000 19.4259 2.3800 0.0000 62 18.7237 6.9501 0.0000 19.6426 2.7471 0.0000 63 18.9747 7.1740 0.0000 19.8560 3.1158 0.0000 64 19.2232 7.4006 0.0000 20.0675 3.4864 0.0000 65 19.4694 7.6300 0.0000 20.2766 3.8579 0.0000 66 19.7128 7.8622 0.0000 20.4845 4.2302 0.0000 67 19.9542 8.0964 0.0000 20.6907 4.6028 0.0000 68 20.1928 8.3334 0.0000 20.8966 4.9763 0.0000 69 20.4294 8.5728 0.0000 21.1013 5.3501 0.0000 70 20.6632 8.8142 0.0000 21.3056 5.7244 0.0000 71 20.8950 9.0580 0.0000 21.5095 6.0987 0.0000 72 21.1248 9.3042 0.0000 21.7130 6.4733 0.0000 73 21.3519 9.5520 0.0000 21.9161 6.8484 0.0000 74 21.5769 9.8021 0.0000 22.1187 7.2234 0.0000 75 21.8000 10.0539 0.0000 22.3214 7.5985 0.0000 76 22.0210 10.3077 0.0000 22.5241 7.9735 0.0000 77 22.2396 10.5630 0.0000 22.7264 8.3486 0.0000 78 22.4563 10.8204 0.0000 22.9287 8.7241 0.0000 79 22.6710 11.0793 0.0000 23.1310 9.0991 0.0000 80 22.8836 11.3403 0.0000 23.3329 9.4746 0.0000 81 23.0943 11.6024 0.0000 23.5348 9.8500 0.0000 82 23.3030 11.8661 0.0000 23.7371 10.2255 0.0000 83 23.5100 12.1315 0.0000 23.9390 10.6009 0.0000 84 23.7151 12.3980 0.0000 24.1409 10.9764 0.0000 85 23.9186 12.6657 0.0000 24.3428 11.3518 0.0000 86 24.1201 12.9351 0.0000 24.5450 11.7273 0.0000 87 24.3200 13.2056 0.0000 24.7469 12.1027 0.0000 88 24.5179 13.4777 0.0000 24.9492 12.4778 0.0000 89 24.7142 13.7506 0.0000 25.1511 12.8533 0.0000 90 24.9093 14.0251 0.0000 25.3534 13.2287 0.0000 91 25.1020 14.3004 0.0000 25.5557 13.6038 0.0000 92 25.2932 14.5773 0.0000 25.7580 13.9792 0.0000 93 25.4827 14.8554 0.0000 25.9603 14.3543 0.0000 94 25.6706 15.1343 0.0000 26.1626 14.7297 0.0000 95 25.8585 15.4132 0.0000 26.3653 15.1048 0.0000 96 26.0461 15.6925 0.0000 26.5676 15.4799 0.0000 97 26.2316 15.9730 0.0000 26.7706 15.8549 0.0000 98 26.4119 16.2571 0.0000 26.8999 16.5990 0.0000 99 26.5991 16.5364 0.0000 26.9745 16.2292 0.0000 100 26.8999 16.5990 0.0000 −0.6667 −1.6642 10.0000 1 −0.6667 −1.6642 10.0000 −0.7816 −2.0919 10.0000 2 −0.4964 −1.3494 10.0000 −0.8120 −2.5332 10.0000 3 −0.2534 −1.0857 10.0000 −0.7493 −2.9713 10.0000 4 0.0347 −0.8718 10.0000 −0.6009 −3.3883 10.0000 5 0.3483 −0.6970 10.0000 −0.3826 −3.7737 10.0000 6 0.6779 −0.5542 10.0000 −0.1129 −4.1252 10.0000 7 1.0162 −0.4345 10.0000 0.1935 −4.4452 10.0000 8 1.3610 −0.3332 10.0000 0.5267 −4.7377 10.0000 9 1.7097 −0.2474 10.0000 0.8798 −5.0062 10.0000 10 2.0616 −0.1748 10.0000 1.2469 −5.2544 10.0000 11 2.4155 −0.1125 10.0000 1.6251 −5.4858 10.0000 12 2.7702 −0.0575 10.0000 2.0117 −5.7025 10.0000 13 3.1261 −0.0068 10.0000 2.4063 −5.9047 10.0000 14 3.4820 0.0415 10.0000 2.8077 −6.0923 10.0000 15 3.8379 0.0890 10.0000 3.2167 −6.2638 10.0000 16 4.1942 0.1361 10.0000 3.6317 −6.4194 10.0000 17 4.5502 0.1839 10.0000 4.0530 −6.5579 10.0000 18 4.9061 0.2326 10.0000 4.4791 −6.6796 10.0000 19 5.2620 0.2821 10.0000 4.9100 −6.7837 10.0000 20 5.6175 0.3328 10.0000 5.3450 −6.8699 10.0000 21 5.9730 0.3846 10.0000 5.7830 −6.9381 10.0000 22 6.3285 0.4381 10.0000 6.2235 −6.9884 10.0000 23 6.6832 0.4944 10.0000 6.6656 −7.0199 10.0000 24 7.0375 0.5530 10.0000 7.1085 −7.0335 10.0000 25 7.3914 0.6149 10.0000 7.5518 −7.0287 10.0000 26 7.7445 0.6799 10.0000 7.9947 −7.0060 10.0000 27 8.0972 0.7481 10.0000 8.4360 −6.9653 10.0000 28 8.4495 0.8199 10.0000 8.8757 −6.9070 10.0000 29 8.8007 0.8953 10.0000 9.3126 −6.8320 10.0000 30 9.1510 0.9747 10.0000 9.7463 −6.7398 10.0000 31 9.5001 1.0585 10.0000 10.1760 −6.6321 10.0000 32 9.8484 1.1463 10.0000 10.6017 −6.5080 10.0000 33 10.1955 1.2389 10.0000 11.0227 −6.3688 10.0000 34 10.5415 1.3362 10.0000 11.4384 −6.2148 10.0000 35 10.8858 1.4380 10.0000 11.8486 −6.0464 10.0000 36 11.2289 1.5449 10.0000 12.2528 −5.8648 10.0000 37 11.5705 1.6566 10.0000 12.6514 −5.6701 10.0000 38 11.9100 1.7735 10.0000 13.0432 −5.4631 10.0000 39 12.2476 1.8960 10.0000 13.4286 −5.2440 10.0000 40 12.5835 2.0233 10.0000 13.8069 −5.0134 10.0000 41 12.9175 2.1562 10.0000 14.1787 −4.7716 10.0000 42 13.2491 2.2946 10.0000 14.5438 −4.5202 10.0000 43 13.5782 2.4383 10.0000 14.9017 −4.2585 10.0000 44 13.9050 2.5871 10.0000 15.2528 −3.9880 10.0000 45 14.2294 2.7415 10.0000 15.5968 −3.7079 10.0000 46 14.5510 2.9015 10.0000 15.9331 −3.4190 10.0000 47 14.8698 3.0667 10.0000 16.2623 −3.1221 10.0000 48 15.1862 3.2375 10.0000 16.5847 −2.8177 10.0000 49 15.4994 3.4134 10.0000 16.8999 −2.5061 10.0000 50 15.8094 3.5942 10.0000 17.2083 −2.1877 10.0000 51 16.1170 3.7805 10.0000 17.5099 −1.8629 10.0000 52 16.4211 3.9712 10.0000 17.8048 −1.5317 10.0000 53 16.7223 4.1671 10.0000 18.0925 −1.1946 10.0000 54 17.0204 4.3678 10.0000 18.3730 −0.8515 10.0000 55 17.3152 4.5729 10.0000 18.6467 −0.5023 10.0000 56 17.6069 4.7824 10.0000 18.9132 −0.1480 10.0000 57 17.8958 4.9962 10.0000 19.1730 0.2111 10.0000 58 18.1811 5.2141 10.0000 19.4263 0.5750 10.0000 59 18.4639 5.4359 10.0000 19.6741 0.9424 10.0000 60 18.7432 5.6618 10.0000 19.9163 1.3139 10.0000 61 19.0197 5.8908 10.0000 20.1541 1.6882 10.0000 62 19.2935 6.1238 10.0000 20.3875 2.0648 10.0000 63 19.5640 6.3600 10.0000 20.6177 2.4439 10.0000 64 19.8317 6.5998 10.0000 20.8444 2.8249 10.0000 65 20.0962 6.8424 10.0000 21.0686 3.2075 10.0000 66 20.3584 7.0886 10.0000 21.2900 3.5914 10.0000 67 20.6173 7.3371 10.0000 21.5099 3.9764 10.0000 68 20.8735 7.5889 10.0000 21.7285 4.3622 10.0000 69 21.1272 7.8435 10.0000 21.9452 4.7489 10.0000 70 21.3782 8.1004 10.0000 22.1614 5.1359 10.0000 71 21.6264 8.3602 10.0000 22.3765 5.5233 10.0000 72 21.8718 8.6223 10.0000 22.5912 5.9115 10.0000 73 22.1152 8.8868 10.0000 22.8050 6.2997 10.0000 74 22.3558 9.1534 10.0000 23.0189 6.6880 10.0000 75 22.5936 9.4227 10.0000 23.2323 7.0766 10.0000 76 22.8294 9.6936 10.0000 23.4450 7.4656 10.0000 77 23.0628 9.9669 10.0000 23.6581 7.8546 10.0000 78 23.2938 10.2418 10.0000 23.8703 8.2437 10.0000 79 23.5224 10.5187 10.0000 24.0826 8.6327 10.0000 80 23.7490 10.7976 10.0000 24.2949 9.0221 10.0000 81 23.9733 11.0781 10.0000 24.5063 9.4115 10.0000 82 24.1955 11.3606 10.0000 24.7182 9.8013 10.0000 83 24.4154 11.6443 10.0000 24.9293 10.1912 10.0000 84 24.6336 11.9300 10.0000 25.1403 10.5810 10.0000 85 24.8499 12.2169 10.0000 25.3514 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100.0000 4.3395 −18.1096 100.0000 19 0.8311 −9.8736 100.0000 4.9460 −18.0254 100.0000 20 1.3634 −9.6788 100.0000 5.5508 −17.9285 100.0000 21 1.8976 −9.4881 100.0000 6.1533 −17.8180 100.0000 22 2.4327 −9.3006 100.0000 6.7534 −17.6947 100.0000 23 2.9685 −9.1159 100.0000 7.3503 −17.5582 100.0000 24 3.5052 −8.9323 100.0000 7.9448 −17.4094 100.0000 25 4.0422 −8.7504 100.0000 8.5353 −17.2482 100.0000 26 4.5793 −8.5688 100.0000 9.1230 −17.0742 100.0000 27 5.1163 −8.3869 100.0000 9.7064 −16.8883 100.0000 28 5.6530 −8.2046 100.0000 10.2861 −16.6904 100.0000 29 6.1896 −8.0214 100.0000 10.8615 −16.4805 100.0000 30 6.7255 −7.8367 100.0000 11.4324 −16.2591 100.0000 31 7.2609 −7.6500 100.0000 11.9990 −16.0261 100.0000 32 7.7956 −7.4612 100.0000 12.5608 −15.7823 100.0000 33 8.3294 −7.2705 100.0000 13.1178 −15.5273 100.0000 34 8.8625 −7.0774 100.0000 13.6700 −15.2620 100.0000 35 9.3948 −6.8815 100.0000 14.2170 −14.9859 100.0000 36 9.9258 −6.6828 100.0000 14.7585 −14.7002 100.0000 37 10.4557 −6.4813 100.0000 15.2947 −14.4042 100.0000 38 10.9844 −6.2770 100.0000 15.8258 −14.0989 100.0000 39 11.5118 −6.0691 100.0000 16.3513 −13.7841 100.0000 40 12.0381 −5.8581 100.0000 16.8712 −13.4605 100.0000 41 12.5632 −5.6434 100.0000 17.3855 −13.1278 100.0000 42 13.0863 −5.4252 100.0000 17.8942 −12.7866 100.0000 43 13.6082 −5.2033 100.0000 18.3973 −12.4371 100.0000 44 14.1281 −4.9775 100.0000 18.8945 −12.0792 100.0000 45 14.6463 −4.7477 100.0000 19.3860 −11.7141 100.0000 46 15.1627 −4.5134 100.0000 19.8720 −11.3411 100.0000 47 15.6774 −4.2752 100.0000 20.3524 −10.9608 100.0000 48 16.1897 −4.0331 100.0000 20.8268 −10.5734 100.0000 49 16.7004 −3.7861 100.0000 21.2956 −10.1792 100.0000 50 17.2083 −3.5347 100.0000 21.7585 −9.7782 100.0000 51 17.7142 −3.2790 100.0000 22.2157 −9.3704 100.0000 52 18.2182 −3.0184 100.0000 22.6674 −8.9567 100.0000 53 18.7189 −2.7531 100.0000 23.1134 −8.5369 100.0000 54 19.2176 −2.4830 100.0000 23.5535 −8.1112 100.0000 55 19.7136 −2.2080 100.0000 23.9884 −7.6795 100.0000 56 20.2068 −1.9283 100.0000 24.4174 −7.2426 100.0000 57 20.6967 −1.6435 100.0000 24.8411 −6.8001 100.0000 58 21.1843 −1.3538 100.0000 25.2592 −6.3524 100.0000 59 21.6687 −1.0589 100.0000 25.6722 −5.9000 100.0000 60 22.1499 −0.7593 100.0000 26.0796 −5.4427 100.0000 61 22.6275 −0.4541 100.0000 26.4814 −4.9803 100.0000 62 23.1023 −0.1440 100.0000 26.8780 −4.5138 100.0000 63 23.5735 0.1712 100.0000 27.2694 −4.0426 100.0000 64 24.0411 0.4920 100.0000 27.6556 −3.5670 100.0000 65 24.5051 0.8175 100.0000 28.0367 −3.0874 100.0000 66 24.9656 1.1483 100.0000 28.4125 −2.6038 100.0000 67 25.4220 1.4847 100.0000 28.7832 −2.1163 100.0000 68 25.8749 1.8258 100.0000 29.1491 −1.6251 100.0000 69 26.3238 2.1721 100.0000 29.5102 −1.1300 100.0000 70 26.7687 2.5237 100.0000 29.8661 −0.6316 100.0000 71 27.2091 2.8804 100.0000 30.2176 −0.1301 100.0000 72 27.6460 3.2422 100.0000 30.5639 0.3751 100.0000 73 28.0782 3.6093 100.0000 30.9058 0.8834 100.0000 74 28.5059 3.9812 100.0000 31.2434 1.3945 100.0000 75 28.9296 4.3578 100.0000 31.5762 1.9088 100.0000 76 29.3486 4.7397 100.0000 31.9045 2.4259 100.0000 77 29.7631 5.1267 100.0000 32.2289 2.9454 100.0000 78 30.1733 5.5181 100.0000 32.5489 3.4677 100.0000 79 30.5791 5.9143 100.0000 32.8649 3.9924 100.0000 80 30.9801 6.3153 100.0000 33.1765 4.5198 100.0000 81 31.3763 6.7207 100.0000 33.4846 5.0493 100.0000 82 31.7681 7.1305 100.0000 33.7890 5.5808 100.0000 83 32.1551 7.5446 100.0000 34.0894 6.1146 100.0000 84 32.5377 7.9628 100.0000 34.3859 6.6505 100.0000 85 32.9160 8.3857 100.0000 34.6787 7.1883 100.0000 86 33.2894 8.8122 100.0000 34.9684 7.7282 100.0000 87 33.6581 9.2427 100.0000 35.2549 8.2696 100.0000 88 34.0228 9.6769 100.0000 35.5378 8.8130 100.0000 89 34.3835 10.1142 100.0000 35.8179 9.3577 100.0000 90 34.7402 10.5550 100.0000 36.0952 9.9039 100.0000 91 35.0933 10.9987 100.0000 36.3693 10.4517 100.0000 92 35.4420 11.4456 100.0000 36.6406 11.0007 100.0000 93 35.7872 11.8953 100.0000 36.9087 11.5513 100.0000 94 36.1287 12.3481 100.0000 37.1741 12.1035 100.0000 95 36.4666 12.8034 100.0000 37.4366 12.6570 100.0000 96 36.8014 13.2610 100.0000 37.6964 13.2116 100.0000 97 37.1330 13.7207 100.0000 37.9545 13.7674 100.0000 98 37.4625 14.1823 100.0000 38.2087 14.3244 100.0000 99 37.7889 14.6456 100.0000 38.2262 14.8750 100.0000 100 38.2262 14.8750 100.0000

It will also be appreciated that the airfoil 52 disclosed in the above Table I may be scaled up or down geometrically for use in other similar turbine designs. Consequently, the coordinate values set forth in Table I may be scaled upwardly or downwardly such that the airfoil profile shape remains unchanged. A scaled version of the coordinates in Table I would be represented by X, Y and Z coordinate values of Table I, with the X, Y and Z non-dimensional coordinate values converted to inches, multiplied or divided by a constant number.

An important term in this disclosure is “profile”. The profile is the range of the variation between measured points on an airfoil surface and the ideal position listed in Table I. The actual profile on a manufactured turbine nozzle will be different than those in Table I and the design is robust to this variation meaning that mechanical and aerodynamic function are not impaired. As noted above, a + or −5% profile tolerance is used herein. The X, Y and Z values are all non-dimensionalized relative to the airfoil height.

The disclosed airfoil shape optimizes and is specific to the machine conditions and specifications. It provides a unique profile to achieve 1) interaction between other stages in the turbine 10; 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical nozzle or airfoil loadings. The disclosed loci of points defined in Table I allow the gas turbine 12 or any other suitable turbine to run in an efficient, safe and smooth manner. As also noted, any scale of the disclosed airfoil 52 may be adopted as long as 1) interaction between other stages in the pressure turbine 10; 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical nozzle or airfoil loadings are maintained in the scaled turbine.

The airfoil 52 described herein thus improves overall gas turbine 12 efficiency. Specifically, the airfoil 52 provides a desired turbine efficiency lapse rate (ISO, hot, cold, part load, etc.). The airfoil 52 also meets all aeromechanics and stress requirements. The turbine nozzle 50 described herein has very specific aerodynamic design requirements such as an upstream bucket radial back pressure (i.e., work splits) and radial velocity triangles for the downstream turbine rotors 150, 250, 350 and 450. Significant cross-functional design effort was require to meet these design goals. The airfoil 52 of the turbine nozzle 50 thus is of a specific shape to meet aerodynamic, mechanical, and heat transfer requirements in an efficient and cost effective manner.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims. 

What is claimed is:
 1. A turbine nozzle comprising an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
 2. The turbine nozzle of claim 1, wherein the turbine nozzle forms part of a stage of a turbine.
 3. The turbine nozzle of claim 1, wherein the turbine nozzle is a fourth stage turbine nozzle.
 4. The turbine nozzle of claim 1, wherein the airfoil shape lies in an envelope within at least one of +/−5% of the X and Y values given in Table 1 and/or +/−5% of a chord length in a direction normal to any airfoil surface location.
 5. The turbine nozzle of claim 1, wherein a height of the turbine nozzle is about 5 inches to about 50 inches in length.
 6. The turbine nozzle of claim 1, wherein the X, Y and Z distances are scalable as a function of a constant or number to provide a scaled-up airfoil and are scalable as a function of the constant or number to provide a scaled-down airfoil.
 7. A turbine nozzle comprising an airfoil having a suction-side uncoated nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete suction-side airfoil shape, the X, Y and Z distances being scalable as a function of a constant or number to provide a scaled-up airfoil and are scalable as a function of the constant or number to provide a scaled-down airfoil.
 8. The turbine nozzle of claim 7, wherein the turbine nozzle forms part of a stage of a turbine.
 9. The turbine nozzle of claim 7, wherein the turbine nozzle is a fourth stage turbine nozzle.
 10. The turbine nozzle of claim 7, wherein the airfoil shape lies in an envelope within at least one of +/−5% of the X and Y values given in Table 1 and/or +/−5% of a chord length in a direction normal to any airfoil surface location.
 11. The turbine nozzle of claim 7, wherein a height of the turbine nozzle is about 5 inches to about 50 inches in length.
 12. A turbine comprising a plurality of turbine nozzles, each of the turbine nozzles comprising an airfoil having an airfoil shape, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
 13. The turbine of claim 12, wherein the plurality of turbine nozzles forms part of a stage of a turbine.
 14. The turbine of claim 12, wherein the plurality of turbine nozzles comprises a plurality of fourth stage turbine nozzles.
 15. The turbine of claim 12, wherein the airfoil shape lies in an envelope within at least one of +/−5% of the X and Y values given in Table 1 and/or +/−5% of a chord length in a direction normal to any airfoil surface location.
 16. The turbine of claim 12, wherein a height the turbine nozzle is about 5 inches to about 50 inches in length.
 17. The turbine of claim 12, wherein the X, Y and Z distances are scalable as a function of a constant or number to provide a scaled-up airfoil and are scalable as a function of the constant or number to provide a scaled-down airfoil.
 18. The turbine of claim 12, wherein X represents a distance parallel to a turbine axis of rotation. 